针对类平板式卫星的结构特点，利用李群上的Lagrange力学和Hamilton力学，分别建立了Euler-Lagrange形式和Hamilton形式的姿态-轨道-结构耦合动力学方程。该方法同时考虑了卫星在轨运行时姿态、轨道与板式结构附件振动间的相互耦合作用，其中板式结构附件的振动通过单自由度扭簧模型进行一阶近似，该描述方式一方面易于通过李群工具对振动现象进行描述，另一方面从Lagrange几何和Hamilton几何的角度推导的动力学方程是全局和无坐标的。此外系统动力学模型的建立考虑了整星质心的时变特性，更为精确。数值算例验证了该建模方法的有效性，通过与刚性模型的仿真对比，分析了类平板式卫星在激励作用下的姿态-轨道-结构耦合效应。结果表明，该模型具有良好的稳定性，能够准确预测激励作用下类平板式卫星在轨运行的动态响应。

This paper focuses on the structural characteristics of plate-type satellites and establishes attitude-orbit-structure coupling dynamic equations in the Euler-Lagrange and Hamilton forms using Lagrange mechanics and Hamilton mechanics on the Lie group， respectively. This method simultaneously considers the coupling effect among the attitude， orbit， and plate structure appendage vibrations of spacecraft in orbit. The vibration phenomenon of the plate structure appendage is approximated by a single degree of freedom torsion spring model. This description method can easily describe the vibration phenomenon through Lie group tools. On the other hand， the dynamic equations derived from the perspectives of Lagrange geometry and Hamilton geometry are global and coordinate free. In addition， the establishment of the system dynamics model considers the time-varying characteristics of the satellite center of mass， making it more accurate. The effectiveness of this modeling method is verified using numerical examples. Through simulation comparison with the rigid model， the attitude-orbit-structure coupling effect of the quasi-plate satellite under excitation is analyzed. Results show that the model has good stability and can accurately predict the dynamic response of the quasi flat satellite in orbit under excitation.